CN106114828A - A kind of double-brake system for aircraft single-wheel brake - Google Patents
A kind of double-brake system for aircraft single-wheel brake Download PDFInfo
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- CN106114828A CN106114828A CN201610436904.8A CN201610436904A CN106114828A CN 106114828 A CN106114828 A CN 106114828A CN 201610436904 A CN201610436904 A CN 201610436904A CN 106114828 A CN106114828 A CN 106114828A
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- wheel
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/42—Arrangement or adaptation of brakes
- B64C25/44—Actuating mechanisms
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60T—VEHICLE BRAKE CONTROL SYSTEMS OR PARTS THEREOF; BRAKE CONTROL SYSTEMS OR PARTS THEREOF, IN GENERAL; ARRANGEMENT OF BRAKING ELEMENTS ON VEHICLES IN GENERAL; PORTABLE DEVICES FOR PREVENTING UNWANTED MOVEMENT OF VEHICLES; VEHICLE MODIFICATIONS TO FACILITATE COOLING OF BRAKES
- B60T13/00—Transmitting braking action from initiating means to ultimate brake actuator with power assistance or drive; Brake systems incorporating such transmitting means, e.g. air-pressure brake systems
- B60T13/10—Transmitting braking action from initiating means to ultimate brake actuator with power assistance or drive; Brake systems incorporating such transmitting means, e.g. air-pressure brake systems with fluid assistance, drive, or release
- B60T13/66—Electrical control in fluid-pressure brake systems
- B60T13/68—Electrical control in fluid-pressure brake systems by electrically-controlled valves
- B60T13/686—Electrical control in fluid-pressure brake systems by electrically-controlled valves in hydraulic systems or parts thereof
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60T—VEHICLE BRAKE CONTROL SYSTEMS OR PARTS THEREOF; BRAKE CONTROL SYSTEMS OR PARTS THEREOF, IN GENERAL; ARRANGEMENT OF BRAKING ELEMENTS ON VEHICLES IN GENERAL; PORTABLE DEVICES FOR PREVENTING UNWANTED MOVEMENT OF VEHICLES; VEHICLE MODIFICATIONS TO FACILITATE COOLING OF BRAKES
- B60T8/00—Arrangements for adjusting wheel-braking force to meet varying vehicular or ground-surface conditions, e.g. limiting or varying distribution of braking force
- B60T8/17—Using electrical or electronic regulation means to control braking
- B60T8/1701—Braking or traction control means specially adapted for particular types of vehicles
- B60T8/1703—Braking or traction control means specially adapted for particular types of vehicles for aircrafts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60T—VEHICLE BRAKE CONTROL SYSTEMS OR PARTS THEREOF; BRAKE CONTROL SYSTEMS OR PARTS THEREOF, IN GENERAL; ARRANGEMENT OF BRAKING ELEMENTS ON VEHICLES IN GENERAL; PORTABLE DEVICES FOR PREVENTING UNWANTED MOVEMENT OF VEHICLES; VEHICLE MODIFICATIONS TO FACILITATE COOLING OF BRAKES
- B60T8/00—Arrangements for adjusting wheel-braking force to meet varying vehicular or ground-surface conditions, e.g. limiting or varying distribution of braking force
- B60T8/32—Arrangements for adjusting wheel-braking force to meet varying vehicular or ground-surface conditions, e.g. limiting or varying distribution of braking force responsive to a speed condition, e.g. acceleration or deceleration
- B60T8/321—Arrangements for adjusting wheel-braking force to meet varying vehicular or ground-surface conditions, e.g. limiting or varying distribution of braking force responsive to a speed condition, e.g. acceleration or deceleration deceleration
- B60T8/325—Systems specially adapted for aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/42—Arrangement or adaptation of brakes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/42—Arrangement or adaptation of brakes
- B64C25/44—Actuating mechanisms
- B64C25/46—Brake regulators for preventing skidding or aircraft somersaulting
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Transportation (AREA)
- Regulating Braking Force (AREA)
Abstract
A kind of double-brake system for aircraft single-wheel brake, is constituted brake anti-sliding control part by wheel spin-up transducer, control box and electrohydraulic servo valve；The brake being used aircraft brake Velocity control to realize brake machine wheel by wheel spin-up transducer, control box and electromagnetic valve selects.Brake system is exported and is divided into little brake gear fluid pressure line and big brake gear fluid pressure line to wheel brake fluid pressure line by the present invention, and make this little brake gear fluid pressure line keep unimpeded, make the break-make of this big brake gear fluid pressure line by controlling device control, and realize aircraft floor and slide the operation of the least brake gear, the function that the whole brake gear of other situations runs, slide in brake carbon mill and damage reaching reduction, improve the purpose improving carbon dish service life.Efficiently solve the difficult problem that the brake carbon brake disc abrasion of existing single-wheel list is big, service life is short, improve service life and the economic benefit of carbon dish.
Description
Technical field
The present invention relates to a kind of airplane wheel brake system, especially, relate to a kind of aircraft single-wheel double-brake have based on
Brake speed selects to slide the brake control system of brake.
Background technology
Aircraft carbon brake uses carbon-to-carbon composite friction material manufacture completely due to brake disc, for the brake of relatively steel, has weight
Measure the advantages such as light, wear-resistant, specific heat is high, high temperature is the most bonding, significantly improve aircraft utilization technical performance and reliance security
Property maintainability economy, thus be used widely on present generation aircraft.Carbon brake is particularly suitable for high-energy brake condition, excellent
Good friction and wear characteristic, gives the long-lived quality of carbon brake disc.But, carbon brake puts into after outfield is run and finds, carbon
Brake disc does not reaches the life value that design is given service life, and have is only about the 60% of value projected life.Carbon dish is caused to make
By the main cause that the life-span is short, present analysis is considered carbon-to-carbon composite friction material to sliding brake bad adaptability, and aircraft is on ground
It is big that wear extent under braking state is slided in face.If the structure that the brake gear of existing brake machine wheel uses " being divided into two " is set
Meter, i.e. single-wheel is equipped with small one and large one two brake gears or double-brake, and little brake is slided for aircraft floor when being used alone
Brake, improves the level that can carry of carbon dish when sliding brake, thus reduces and slide carbon mill damage in brake, improve and improve making of carbon dish
With the life-span, other situations two brake or double-brake use as set of device simultaneously.
Airplane wheel brake system is used for brake control and the anti-sliding control of airplane wheel, wide variety of on current aircraft
It it is electronic anti-skid braking system.Airplane wheel brake system mainly includes handling adnexa, detection accessory and control adnexa, for often
The hydraulic brake system of rule, mainly includes water brake valve, electrohydraulic servo valve, wheel spin-up transducer, control box.With regard to a machine
For wheel, the brake machine wheel that electronic anti-skid braking system is controlled is the what is called on a wheel with a disc brake device
Single brake machine wheel, even if some aged aircrafts are equipped with two hose type brake gears for meeting braking ability on a wheel
So-called double-brake wheel, two of this double-brake wheel brakes are also controlled by brake system to run simultaneously.For solving carbon
The problem in service life of dish, selects to use the requirement of brake according to single-wheel double-brake, and existing airplane wheel brake system does not has
This ability.
Summary of the invention
For overcoming the deficiency that can not select brake modes present in prior art, the present invention proposes a kind of for aircraft
The double-brake system of single-wheel brake.
The present invention includes water brake valve, controls box, electrohydraulic servo valve, electromagnetic valve and wheel spin-up transducer.Therein
Wheel spin-up transducer, control box and electrohydraulic servo valve constitute brake anti-sliding control part；Wheel spin-up transducer, control box and
The brake that electromagnetic valve uses aircraft brake Velocity control to realize brake machine wheel selects: individually select little brake gear to run, with
Realize the part brake of airplane wheel；Or select little brake gear to run with big brake gear, it is achieved airplane wheel simultaneously
All brakes.
Described aircraft brake Velocity control selectively brake formula is expressed as follows:
I (V)=0, as 0 V Vd
I (V)=1, as V >=VdOr V=0
In formula, I (V) controls box and controls electric current to electromagnetic valve output, and numeral 1 represents has electric current to export, and numeral 0 represents nothing
Electric current exports.
V aircraft brake speed；VdAircraft brake speed setting value, value is 40～65Km/h.Described water brake
Valve is arranged on below cockpit floor, driver handle it, the water brake pressure needed for output.The three of water brake valve
Individual hydraulic interface is hydraulic interface oil-in, hydraulic interface brake mouth and hydraulic interface oil return opening respectively.Hydraulic interface oil-in
Coupling with airplane brake system pressure source pipeline, hydraulic interface brake mouth couples with electrohydraulic servo valve oil-in pipeline, and hydraulic pressure connects
Mouth oil return opening couples with aircraft return line.
The electrical outlets of described electrohydraulic servo valve is implemented electrically to couple with controlling box by cable, receives and controls what box was sent
Brake anti-sliding control current signal.Three hydraulic interfaces of described electrohydraulic servo valve are electrohydraulic servo valve oil-in, electro-hydraulic respectively
Servo valve brake mouth and electrohydraulic servo valve oil return opening；Wherein: described electrohydraulic servo valve oil-in and the brake mouth of water brake valve
Pipeline couples；Electrohydraulic servo valve oil return opening couples with aircraft return line；Electrohydraulic servo valve brake mouth by pipeline respectively with machine
The big brake gear oil-feed interface of wheel and little brake gear oil-feed interface couple, specifically by described electrohydraulic servo valve brake mouth
Connecting pipeline is divided into little brake gear fluid pressure line and big brake gear fluid pressure line；Little brake gear fluid pressure line therein is straight
Connect the little brake gear oil-feed interface with wheel to couple；Big brake gear fluid pressure line therein enters with the big brake gear of wheel
Oil interface couples, and is serially connected with electromagnetic valve at described big brake gear fluid pressure line；Going out of described big brake gear fluid pressure line
Hydraulic fluid port and big brake gear oil-feed orifice.
The electric interfaces of described electromagnetic valve is electrically coupled with the electric interfaces outfan controlling box by shielding insulation wire,
Specifically by the electromagnet coil of electromagnetic valve with control box electric interfaces outfan electrically couple, by control box control power supply or
Send control current signal.Three hydraulic interfaces of this electromagnetic valve are respectively electromagnetic valve oil-in, electromagnetic valve oil-out and electromagnetism
Valve oil return opening.Described electromagnetic valve oil-in is coupled with the brake mouth with electrohydraulic servo valve by pipeline, and electromagnetic valve oil-out passes through
Big brake gear fluid pressure line couples with the big brake gear oil-feed interface of brake machine wheel；Oil return opening joins with aircraft return line
Connect.
Wheel spin-up transducer is arranged on plane axletree, or on wheel braking housing, by mechanically operated mode with
Wheel couples, and to experience wheel rotary speed, wheel rotary speed is converted to signal of telecommunication output.Described wheel spin-up transducer
Electric interfaces by cable with control box electrically couple, the wheel rotary speed voltage signal detected is supplied to control
Box, the sliding mode of monitoring wheel.
The input of the electric interfaces of described control box and velocity sensor are by cable connection, to receive velocity sensor
The wheel rate signal provided；The outfan of the electric interfaces controlling box passes through cable connection with electrohydraulic servo valve, watches to electro-hydraulic
Take valve and send control signal.Control box electric interfaces outfan also with electromagnetic valve cable connection, send control to electromagnetic valve
Signal processed；Control brake speed setting value V of electric current to electromagnetic valve output by described control boxdIt is 40～65Km/h.
The present invention uses the way of " being divided into two ", brake system is exported to wheel brake fluid pressure line
It is divided into little brake gear fluid pressure line and big brake gear fluid pressure line, and makes this little brake gear fluid pressure line keep unimpeded,
Make the break-make of this big brake gear fluid pressure line by controlling device control, and realize aircraft floor slide the least brake gear fortune
OK, the function that the whole brake gear of other situations runs, slides in brake carbon mill and damages reaching reduction, improve and improve carbon dish and makes
By the purpose in life-span.
In the present invention, by wheel spin-up transducer, control box and electrohydraulic servo valve constitutes brake anti-sliding control part；Wheel
Velocity sensor, controls box and electromagnetic valve is used for realizing brake and selects.
Brake selects by electromagnetic valve, controls box and wheel spin-up transducer composition control device, when using aircraft brake
Ground movement speed i.e. brake speed control methods carries out oil circuit and opens and closes control realization: when brake speed is less than setting value, according to
The rate signal that wheel spin-up transducer gathers, controls box and does not controls electric current to electromagnetic valve output, and electromagnetic valve is not powered and located
In cut-off or closed mode, electromagnetic valve does not has hydraulic coupling to export；When brake speed is more than or equal to setting value, or i.e. speed shut down by aircraft
When degree is zero, controlling box and send control signal to electromagnetic valve or provide electric energy, electromagnetic valve obtains for electrically activating and being in unlatching shape
State, the fluid pressure line that electromagnetic valve controls is open-minded, and electromagnetic valve has hydraulic coupling to export.
Electromagnetic valve is arranged on the big brake gear fluid pressure line of electrohydraulic servo valve brake mouth output, controls by controlling box
Realize electromagnetic valve oil-feed oil circuit and the communication of fuel-displaced oil circuit and disconnection, thus control electromagnetic valve place fluid pressure line whether export and
Disconnect brake pressure.The electromagnet coil of this electromagnetic valve electrically couples with the electric interfaces outfan controlling box, by controlling box control
System is powered or sends control current signal, and the unlatching of electromagnetic valve is controlled by control box, and controls box and be controlled by wheel speed biography
The airplane wheel brake speed of sensor impression, when brake speed is less than setting value, controlling box does not provides control electricity to electromagnetic valve
Stream, electromagnetic valve is not energized and is off, and electromagnetic valve oil-out does not export, and oil-out and oil return opening are linked up；When stopping
When vehicle speed is more than or equal to setting value, or brake speed is zero, and controlling box provides control electric current, solenoid valves to electromagnetic valve
Opening, electromagnetic valve oil return mouth is closed, and oil-in and oil-out are linked up, and the fluid pressure line that electromagnetic valve controls is open-minded.
The present invention is suitable for use with the single-wheel double-brake wheel of carbon brake, can meet single-wheel double-brake and select to use brake
Requirement.Owing to native system has the ability selecting to slide brake, so, when aircraft floor slides brake, only with little brake dress
Put or brake gear runs rather than all brake gears are the most all running, improve the energy of carbon dish when sliding brake
Load level, thus avoid the short slab that carbon-to-carbon composite friction material brake disc low speed mental retardation brake wear extent is excessive, make to slide and stop
Carbon dish wear extent during car reduces, and reaches to improve or improve the purpose in carbon dish service life.Designed by this wheel and system,
Have adjusted the use state of carbon dish, make the anti abrasive good characteristic of carbon-to-carbon composite friction material be given full play of, effectively
Solve the difficult problem that the brake carbon brake disc abrasion of existing single-wheel list is big, service life is short, improve service life and the warp of carbon dish
Ji benefit.
Accompanying drawing explanation
Accompanying drawing 1 is the structural representation of the present invention.In figure:
1. water brake valve；2. electrohydraulic servo valve；3. control box；4. wheel spin-up transducer；5. brake machine wheel；6. electromagnetism
Valve；The least brake gear fluid pressure line；8. big brake gear fluid pressure line；The least brake gear oil-feed interface；Brake the most greatly dress
Put oil-feed interface.
Detailed description of the invention
The present embodiment is a kind of double-brake system for aircraft single-wheel brake.
See accompanying drawing 1.Described brake system is that conventional hydraulic is handled.Main landing gear is equipped with a brake machine wheel, with two
Individual brake gear, referred to as single-wheel double-brake wheel.The brake disc of brake gear uses carbon-to-carbon composite friction material manufacture completely.
The brake disc number of a brake gear in said two brake gear is less, and braking for single disc-type or double plate fills
Put, make heat reservoir axial dimension little, therefore the least brake gear；Another brake gear brake disc number is more, for multiple-disc brake
Device, makes heat reservoir axial dimension big, therefore the biggest brake gear.Described little brake gear and big brake gear are all disclosed in
In the innovation and creation of Application No. 201610281025.2:
The heat reservoir of described little brake gear is made up of compression plate, bearing disc and Moving plate, and Moving plate quantity is 1～2 dishes, for single-deck
Formula or double plate brake；Compression plate therein is adjacent with described cylinder block, a card of bearing disc be positioned in brake shell
End surfaces laminating of housing bearing disc, Moving plate is between described compression plate and bearing disc.Described little brake is individually grasped
Brake for ground taxi time vertical.
The heat reservoir of described big brake gear is made up of compression plate, bearing disc, multiple Moving plate and multiple quiet dish；Described Moving plate
Quantity is 3～5 dishes, for multiple-disc brake device；Described compression plate is adjacent with cylinder block, and a card of bearing disc is stopped with being positioned at
One end surfaces laminating of the housing bearing disc on car housing；Multiple Moving plates and multiple quiet dish are with Moving plate-quiet dish-Moving plate-quiet
The interleaved mode of dish is arranged between described compression plate and bearing disc.
The present embodiment includes water brake valve 1, controls box 3, electrohydraulic servo valve 2, electromagnetic valve 6 and wheel spin-up transducer 4.
Wheel spin-up transducer 4 therein, control box 2 and electrohydraulic servo valve 2 constitute brake anti-sliding control part；Wheel spin-up transducer
4, control box 3 and electromagnetic valve 6 to select for the brake realizing brake machine wheel 5: individually select little brake gear to run, with achievement unit
Divide brake；Or select little brake gear to run with big brake gear, it is achieved all to brake simultaneously.
Described water brake valve 1 is arranged on below cockpit floor, driver handle it, and the hydraulic pressure needed for output is stopped
Car pressure.Water brake valve 1 has three hydraulic interfaces, is that hydraulic interface oil-in, hydraulic interface brake mouth and hydraulic pressure connect respectively
Mouth oil return opening.Hydraulic interface oil-in couples with airplane brake system pressure source pipeline, hydraulic interface brake mouth and electro-hydraulic servo
Valve 2 oil-in pipeline couples, and hydraulic interface oil return opening couples with aircraft return line.
Electrohydraulic servo valve 2 has an electrical outlets and three hydraulic interfaces.Described electrical outlets passes through connectorized cable
Implement electrically to couple with controlling box 3, receive and control the brake anti-sliding control current signal that box 3 is sent.Described three hydraulic interfaces
It is electrohydraulic servo valve oil-in, electrohydraulic servo valve brake mouth and electrohydraulic servo valve oil return opening respectively；Wherein:
Described electrohydraulic servo valve oil-in couples with the brake mouth pipeline of water brake valve 1；Electrohydraulic servo valve brake mouth leads to
Cross pipeline to couple, specifically by described electro-hydraulic with big brake gear oil-feed interface and the little brake gear oil-feed interface of wheel respectively
The connecting pipeline of servo valve brake mouth is divided into little brake gear fluid pressure line 7 and big brake gear fluid pressure line 8 through three way cock；
Little brake gear fluid pressure line 7 therein directly couples with the little brake gear oil-feed interface 9 of wheel；Big brake gear therein
Fluid pressure line 8 couples with the big brake gear oil-feed interface 10 of wheel, and is serially connected with electricity at described big brake gear fluid pressure line 8
Magnet valve 6, the oil-in of the most described electromagnetic valve 6 is connected with the brake mouth of electrohydraulic servo valve 2 by pipeline, the oil-out of this electromagnetic valve
Connect with the oil-in of big brake gear fluid pressure line 8；The oil-out of described big brake gear fluid pressure line 8 and big brake gear
Oil-feed interface 10 connects.
Electromagnetic valve 6 be arranged on electrohydraulic servo valve 2 brake mouth output another fluid pressure line 8 on, by control box 3 control
Realize electromagnetic valve 6 oil-feed oil circuit and the communication of fuel-displaced oil circuit and disconnection, thus it is the most defeated to control electromagnetic valve 6 place fluid pressure line 8
Go out and disconnect brake pressure.Electromagnetic valve 6 has an electric interfaces and three hydraulic interfaces；Three described hydraulic interfaces are respectively
Electromagnetic valve oil-in, electromagnetic valve oil-out and electromagnetic valve oil return mouth.
Described electromagnetic valve oil-in couples with the brake mouth pipeline of electrohydraulic servo valve 2, electromagnetic valve oil-out and brake machine wheel 5
Big brake gear oil-feed interface 10 pipeline couple, oil return opening couples with aircraft return line.
Described electric interfaces is electrically coupled, specifically with the electric interfaces outfan controlling box 3 by shielding insulation wire
The electromagnet coil of electromagnetic valve 6 is electrically coupled with the electric interfaces outfan controlling box 3, is controlled power supply by controlling box 3 or send out
Go out to control current signal.The unlatching of electromagnetic valve 6 is controlled by control box 3, and controls box 3 and be controlled by wheel spin-up transducer 4 and feel
The airplane wheel brake speed being subject to, when brake speed is less than setting value, controlling box 3 does not provides control electric current, electricity to electromagnetic valve 6
Magnet valve 6 is not energized and is off, and electromagnetic valve 6 oil-out does not export, and oil-out and oil return opening are linked up；When brake speed
When degree is more than or equal to setting value, or brake speed is zero, controls box 3 and controls electric current to electromagnetic valve 6 offer, and electromagnetic valve 6 is energized
Opening, electromagnetic valve 6 oil return opening is closed, and oil-in and oil-out are linked up, and the fluid pressure line 8 that electromagnetic valve 6 controls is open-minded.
Brake speed is the brake of zero, is a kind of braking conditions of being under stopped status of aircraft, shuts down such as take-off line and stops
Car, airplane parking area shutdown brake, at this moment need whole brake gear to enable.
Wheel spin-up transducer 4 is arranged on plane axletree, or on wheel braking housing, by mechanically operated mode with
Wheel couples, and to experience wheel rotary speed, wheel rotary speed is converted to signal of telecommunication output.In the present embodiment, wheel speed
Degree sensor 4 is arranged on plane axletree, brake machine wheel 5 hub drive pin be rotated.Described wheel spin-up transducer 4 has
One electric interfaces, is electrically coupled with controlling box 3 by cable, and the wheel rotary speed voltage signal detected is supplied to control
Box 3 processed, the sliding mode of monitoring wheel.
Control box 3 and there is brake anti-sliding control and fault detection capability.Control input and the speed of the electric interfaces of box 3
Sensor 4 is by cable connection, to receive the wheel rate signal that velocity sensor 4 provides；Control electric interfaces defeated of box 3
Go out end with electrohydraulic servo valve 2 by cable connection, send control signal to electrohydraulic servo valve 2.Control electric interfaces defeated of box 3
Go out end also with electromagnetic valve 6 cable connection, send control signal to electromagnetic valve 6；Control box 3 to be powered by aircraft power system.
Described brake speed setting value V being exported control electric current by control box 3 to electromagnetic valve 6dIt is 40～65Km/h；This reality
Executing example is 48Km/h；
In the present embodiment, Article 1 brake passage i.e. fluid pressure line 7 is unblocked, it is ensured that can be used in brake at any time；The
Article two, brake passage i.e. fluid pressure line 8 is with good conditionsi open-minded.So, described brake system ensure that aircraft floor slides brake
Time only use little brake gear, in the case of other, little brake gear uses with big brake gear simultaneously, it is achieved the double-brake to aircraft.
Brake process skids if there is wheel, by controlling box 3, electrohydraulic servo valve 2 and wheel spin-up transducer 4 structure
The brake anti-sliding control part become is implemented to control.Anti-sliding control is realized by prior art.
Select brake by electromagnetic valve 6, control box 3 and wheel spin-up transducer 4 three adnexa composition control device, use aircraft
During brake, ground movement speed i.e. brake speed control methods carries out oil circuit keying control realization；When brake speed is less than setting value
Time, the rate signal gathered according to wheel spin-up transducer 4, control box 3 and do not control electric current to electromagnetic valve 6 output, electromagnetic valve 6 does not has
Having power supply to be in cut-off or closed mode, electromagnetic valve 6 does not has hydraulic coupling to export；When brake speed is more than or equal to setting value, or
Aircraft is in stopped status speed when being zero, controls box 3 and sends control signal to electromagnetic valve 6 or provide electric energy, and electromagnetic valve 6 obtains
For electrically activating and being in opening, the fluid pressure line that electromagnetic valve 6 controls is open-minded, and electromagnetic valve 6 has hydraulic coupling to export.
Aircraft brake Velocity control selectively brake formula is used to be expressed as follows:
I (V)=0, as 0 V Vd
I (V)=1, as V >=VdOr V=0
In formula, I (V) controls box and controls electric current to electromagnetic valve output, and numeral 1 represents has electric current to export, and numeral 0 represents nothing
Electric current exports.
V aircraft brake speed；VdAircraft brake speed setting value, value is 40～65Km/h；
Wheel velocity measuring is completed by wheel spin-up transducer 4 adnexa, the sliding mode of monitoring wheel；Anti-sliding control is by controlling
Box 3 processed completes；Electrohydraulic servo valve 2 response controls the control current signal of box 3, exports and regulate the brake transporting to brake machine wheel 5
Pressure；Selectively brake and carried out by electromagnetic valve 6, control box 3 and wheel spin-up transducer 4 three adnexa composition control device.
The rate signal of wheel spin-up transducer 4 detection, reflects the sliding race of aircraft or ground taxi speed；If wheel is fast
Degree sensor 4 lost efficacy, and the rate signal also having another undercarriage wheel spin-up transducer is available, or aircraft floor slides
Rate signal is provided by FDR system.
Claims (7)
1., for a double-brake system for aircraft single-wheel brake, the main landing gear of aircraft is equipped with a brake machine wheel, this brake
Wheel has little brake gear and big brake gear, it is characterised in that includes water brake valve, control box, electrohydraulic servo valve, electromagnetism
Valve and wheel spin-up transducer；Wheel spin-up transducer therein, control box and electrohydraulic servo valve constitute brake anti-sliding control portion
Point；The brake that wheel spin-up transducer, control box and electromagnetic valve use aircraft brake Velocity control to realize brake machine wheel selects:
Little brake gear is individually selected to run, to realize the part brake of airplane wheel；Or select little brake gear and the dress that brakes greatly
Put and run simultaneously, it is achieved whole brakes of airplane wheel.
2. as claimed in claim 1 for the double-brake system of aircraft single-wheel brake, it is characterised in that described water brake valve is pacified
It is contained in below cockpit floor, driver it is handled, the water brake pressure needed for output；Three liquid of water brake valve
Crimping mouth is hydraulic interface oil-in, hydraulic interface brake mouth and hydraulic interface oil return opening respectively；Hydraulic interface oil-in with fly
Machine brake system pressure source pipeline couples, and hydraulic interface brake mouth couples with electrohydraulic servo valve oil-in pipeline, and hydraulic interface returns
Hydraulic fluid port couples with aircraft return line.
3. as claimed in claim 1 for the double-brake system of aircraft single-wheel brake, it is characterised in that described electrohydraulic servo valve
Electrical outlets is implemented electrically to couple with controlling box by cable, receives and controls the brake anti-sliding control current signal that box is sent；Institute
Three hydraulic interfaces stating electrohydraulic servo valve are electrohydraulic servo valve oil-in, electrohydraulic servo valve brake mouth and electrohydraulic servo valve respectively
Oil return opening；Wherein: described electrohydraulic servo valve oil-in couples with the brake mouth pipeline of water brake valve；Electrohydraulic servo valve oil return opening
Couple with aircraft return line；Electrohydraulic servo valve brake mouth by pipeline respectively with the big brake gear oil-feed interface of wheel and little
Brake gear oil-feed interface couples, and specifically the connecting pipeline of described electrohydraulic servo valve brake mouth is divided into little brake gear hydraulic pressure
Pipeline and big brake gear fluid pressure line；The direct little brake gear oil-feed with wheel of little brake gear fluid pressure line therein connects
Mouth couples；Big brake gear fluid pressure line therein couples with the big brake gear oil-feed interface of wheel, and in described big brake
Device fluid pressure line is serially connected with electromagnetic valve；The oil-out of described big brake gear fluid pressure line is with big brake gear oil-feed interface even
Logical.
4. as claimed in claim 1 for the double-brake system of aircraft single-wheel brake, it is characterised in that described electromagnetic valve electric
Interface is electrically coupled, specifically by the electromagnetism iron wire of electromagnetic valve with the electric interfaces outfan controlling box by shielding insulation wire
The electric interfaces outfan enclosed and control box electrically couples, and is controlled power supply by controlling box or sends control current signal；This electromagnetism
Three hydraulic interfaces of valve are respectively electromagnetic valve oil-in, electromagnetic valve oil-out and electromagnetic valve oil return mouth；Described electromagnetic valve oil-feed
Mouth is coupled with the brake mouth with electrohydraulic servo valve by pipeline, and electromagnetic valve oil-out is by big brake gear fluid pressure line and brake
The big brake gear oil-feed interface of wheel couples；Oil return opening couples with aircraft return line.
5. as claimed in claim 1 for the double-brake system of aircraft single-wheel brake, it is characterised in that wheel spin-up transducer is pacified
It is contained on plane axletree, or on wheel braking housing, is coupled with wheel by mechanically operated mode, to experience wheel rotation speed
Degree, is converted to signal of telecommunication output by wheel rotary speed；The electric interfaces of described wheel spin-up transducer passes through cable and control
Box electrically couples, and the wheel rotary speed voltage signal detected is supplied to control box, the sliding mode of monitoring wheel.
6. as claimed in claim 1 for the double-brake system of aircraft single-wheel brake, it is characterised in that described control box electric
The input of interface and velocity sensor are by cable connection, to receive the wheel rate signal that velocity sensor provides；Control
The outfan of the electric interfaces of box and electrohydraulic servo valve, by cable connection, send control signal to electrohydraulic servo valve；Control box
Electric interfaces outfan also with electromagnetic valve cable connection, send control signal to electromagnetic valve；By described control box to electricity
Magnet valve output controls brake speed setting value V of electric currentdIt is 40～65Km/h.
7. as claimed in claim 1 for the double-brake system of aircraft single-wheel brake, it is characterised in that
Described aircraft brake Velocity control selectively brake formula is expressed as follows:
I (V)=0, as 0 V Vd
I (V)=1, as V >=VdOr V=0
In formula, I (V) controls box and controls electric current to electromagnetic valve output, and numeral 1 represents has electric current to export, and numeral 0 represents no current
Output；V aircraft brake speed；VdAircraft brake speed setting value, value is 40～65Km/h.
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| CN201610436904.8A CN106114828B (en) | 2016-06-17 | 2016-06-17 | A kind of double-brake system for aircraft single-wheel brake |
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| CN201610436904.8A CN106114828B (en) | 2016-06-17 | 2016-06-17 | A kind of double-brake system for aircraft single-wheel brake |
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| CN106114828A true CN106114828A (en) | 2016-11-16 |
| CN106114828B CN106114828B (en) | 2018-02-06 |
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| CN201610436904.8A Expired - Fee Related CN106114828B (en) | 2016-06-17 | 2016-06-17 | A kind of double-brake system for aircraft single-wheel brake |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107628010A (en) * | 2017-09-01 | 2018-01-26 | 金勇� | Without power-assisted hydraulic control brake system |
| CN109319094A (en) * | 2018-11-19 | 2019-02-12 | 西安航空制动科技有限公司 | Take off line brake bootstrap method and brake-by-wire system |
| CN109319095A (en) * | 2018-11-19 | 2019-02-12 | 西安航空制动科技有限公司 | Enhance the aircraft brake-by-wire system and control method of take-off line braking ability |
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| DE4112137A1 (en) * | 1991-04-13 | 1992-10-15 | Bosch Gmbh Robert | HYDRAULIC FOREIGN BRAKE SYSTEM WITH ANTI-BLOCKING PROTECTION AND DRIVE-SLIP CONTROL DEVICE, ESPECIALLY FOR MOTOR VEHICLES |
| JP2001048000A (en) * | 1999-08-10 | 2001-02-20 | Nisshinbo Ind Inc | Antilock brake control device |
| CN202624192U (en) * | 2012-06-18 | 2012-12-26 | 中国航空工业集团公司西安飞机设计研究所 | Antiskid brake control system for airplane |
| CN104760692A (en) * | 2015-04-01 | 2015-07-08 | 西安航空制动科技有限公司 | Normal aircraft brake system |
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2016
- 2016-06-17 CN CN201610436904.8A patent/CN106114828B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE4112137A1 (en) * | 1991-04-13 | 1992-10-15 | Bosch Gmbh Robert | HYDRAULIC FOREIGN BRAKE SYSTEM WITH ANTI-BLOCKING PROTECTION AND DRIVE-SLIP CONTROL DEVICE, ESPECIALLY FOR MOTOR VEHICLES |
| JP2001048000A (en) * | 1999-08-10 | 2001-02-20 | Nisshinbo Ind Inc | Antilock brake control device |
| CN202624192U (en) * | 2012-06-18 | 2012-12-26 | 中国航空工业集团公司西安飞机设计研究所 | Antiskid brake control system for airplane |
| CN104760692A (en) * | 2015-04-01 | 2015-07-08 | 西安航空制动科技有限公司 | Normal aircraft brake system |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107628010A (en) * | 2017-09-01 | 2018-01-26 | 金勇� | Without power-assisted hydraulic control brake system |
| CN109319094A (en) * | 2018-11-19 | 2019-02-12 | 西安航空制动科技有限公司 | Take off line brake bootstrap method and brake-by-wire system |
| CN109319095A (en) * | 2018-11-19 | 2019-02-12 | 西安航空制动科技有限公司 | Enhance the aircraft brake-by-wire system and control method of take-off line braking ability |
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|---|---|
| CN106114828B (en) | 2018-02-06 |
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